基于解析控制律的太阳帆星际转移轨道控制

太阳帆航天器可依靠反射太阳光子提供动力,因此较适用于远距离的星际转移任务.针对太阳帆航天器星际转移轨道控制问题,提出一种新的解析最优控制律,通过设定混合权重对各轨道根数进行联合控制.引入改进春分点轨道根数对解析控制律进行了优化推导,并以水星探测任务为背景进行了相应的仿真分析.仿真结果表明,该控制律计算速度较快,可对各个轨道根数进行联合控制,从而得到满足工程要求的太阳帆航天器星际转移轨道.     

深空探测柔性太阳帆航天器动力学建模与姿态控制

太阳帆利用太阳辐射压力提供太空航行的必要动力,由于具有理论上的无限速度和无需消耗任何燃料等优势,被认为是完成未来深空探测任务的有效技术途径之一.柔性太阳帆航天器的动力学模型包括多体动力学、刚柔耦合动力学和太阳辐射光压模型,复杂的动力学特性导致其姿态控制设计具有很强的挑战性.针对带有控制杆的柔性太阳帆航天器,本文采用拉格朗日方程和有限元法,给出了面向控制的解析式动力学模型.所推导的刚柔耦合动力学模型,刻画了太阳帆航天器的本质动力学特性,即双框架控制杆的短周期运动,姿态与柔性太阳帆的耦合效应,以及在太阳光压恢复力矩下的姿态静稳定性和长周期运动.基于带控制杆的太阳帆航天器的双时间尺度特性,提出了双回路控制结构,用于实现航天器俯仰轴和偏航轴的姿态控制.将内回路设计为PD控制器,用于实现质心位置的调整.将外回路设计为PID控制器,用于阻尼姿态运动,并实现在平衡太阳光压力矩下的姿态保持.从而将柔性太阳帆航天器的复杂姿态控制问题转化为两个低阶子问题,实现了在不同频带上的控制设计.仿真结果验证了动力学建模和姿态控制设计方法的有效性.     

基于小波逼近的航天器太阳帆板展开过程最优控制的遗传算法

本文讨论了航天器太阳帆板展开过程中航天器姿态的最优控制问题，在控制算法中用小波函数逼近控制输入规律，提出了太阳巾帆板展开过程最优控制的遗传算法，数值仿真表明，小波逼近和遗传算法联合求解最优控制问题是有效的。     

低地球轨道航天器表面计算仿真

现代战争中航天器发挥着越来越重要的作用,同时航天器表面带电造成的危害也越来越明显.利用航天器与等离子体相互作用系统软件SPIS,采用PIC粒子分室法模拟计算了低轨道航天器表面及周围等离子体电位分布,航天器表面电子、离子及二次电子电荷密度分布,总结了航天器表面充电特性规律.结果表明:由于等离子体温度低、浓度高,航天器表面带电的电位较低;航天器运动方向前方,等离子体电位较高,在航天器运动方向背侧,等离子体电位较低;航天器周围的等离子体环境受尾迹效应的影响显著.仿真结果为航天器表面带电问题研究及航天器表面带电防护技术提供了技术参考.     

基于两相幂次趋近律的航天器姿态控制

针对带有系统不确定性的航天器姿态控制系统,提出一种基于两相幂次趋近律的姿态控制方法.在趋近律设计中,根据滑模变量值的变化调整趋近律的幂次值,确保滑模变量在远离滑模面和接近滑模面时均具有更快的收敛速度.同时,通过分别计算两个趋近阶段的收敛时间,可直接获得较为准确的滑模变量收敛时间表达式.此外,在控制器设计中采用鲁棒项补偿...     

特定条件的二阶系统的最优控制解析解

针对给控制对象或控制过程加以外部和内部控制作用,使控制对象或控制过程按照某种最优化方法进行,这种最优方式用一个人为确定的目标函数或性能指标为最优来表示。求解了在指定端点固定条件以及目标函数情况下二阶系统的最优控制解析解。以二阶RLC串联充电电路为例,讨论了在指定时间内对电容充电到指定电压,同时在充电过程中保证充电电压最小,发热量最小的最优控制,对控制系统设计有一定指导意义。     

CG伪谱法在欠驱动航天器姿态机动最优控制中的应用

使用Chebyshev-Gauss(CG)伪谱法研究带动量轮和推力器的欠驱动航天器姿态最优控制问题.基于欧拉姿态角和动量矩定理导出两类航天器姿态运动模型,采用Clenshaw-Curtis积分近似得到性能指标函数中的积分项,应用重心拉格朗日插值逼近状态变量和控制变量,将连续最优控制问题离散为具有代数约束的非线性规划(NLP)问题,通过序列二次规划(SQP)算法求解.数值仿真结果表明,对两类欠驱动航天器的姿态机动最优控制均能达到设计控制要求,得到的姿态最优曲线与验证得到的曲线几乎完全重叠.     

基于解析法和遗传算法的机械手运动学逆解

研究优化机械手轨迹规划问题,机械手运动时要具有稳定性避障性能。针对平面3自由度冗余机械手优化控制问题,建立机械手的结构模型。提出用解析法和遗传算法相结合满足具有计算量小和适应性强的特点。在给定机械手末端执行器的运动轨迹,按着机械手冗余自由度,运动轨迹上每个点对应的关节角有无穷多个解。而通过算法可以找到一组最优的关节角,可得到优化机械手运动过程中柔顺性和避障点。仿真结果表明,该算法可以快速收敛到全局最优解,可用于计算冗余机械手运动学逆解,并可实现机器人的轨迹规划和避障优化控制。     

Optimal guidance law for cooperative attack of multiple missiles based on optimal control theory

This article considers the problem of optimal guidance laws for cooperative attack of multiple missiles based on the optimal control theory. New guidance laws are presented such that multiple missiles attack a single target simultaneously. Simulation results show the effectiveness of the proposed algorithms.     

Successive Chebyshev pseudospectral convex optimization method for nonlinear optimal control problems

This article aims at proposing a successive Chebyshev pseudospectral convex optimization method for solving general nonlinear optimal control problems (OCPs). First, Chebyshev pseudospectral discrete scheme is used to discretize a general nonlinear OCP. At the same time, a convex subproblem is formulated by using the first-order Taylor expansion to convexify the discretized nonlinear dynamic constraints. Second, a trust-region penalty term is added to the performance index of the subproblem, and a successive convex optimization algorithm is proposed to solve the subproblem iteratively. Noted that the trust-region penalty parameters can be adjusted according to the linearization error in iterative process, which improves convergence rate. Third, the Karush–Kuhn–Tucker conditions of the subproblem are derived, and furthermore, a proof is given to show that the algorithm will iteratively converge to the subproblem. Additionally, the global convergence of the algorithm is analyzed and proved, which is based on three key lemmas. Finally, the orbit transfer problem of spacecraft is used to test the performance of the proposed method. The simulation results demonstrate the optimal control is bang-bang form, which is consistent with the result of theoretical proof. Also, the algorithm is of efficiency, fast convergence rate, and high accuracy. Therefore, the proposed method provides a new approach for solving nonlinear OCPs online and has great potential in engineering practice.     

Economically optimal batch diafiltration via analytical multi-objective optimal control

This paper studies the problem of economically oriented optimal operation of batch membrane diafiltration processes that are designed to concentrate the valuable components of the solution and to purge the impurities from it. We consider a complex economical objective that accounts for the total operational costs comprising a cost of consumed diluant, costs related to duration of processing, and a cost of product loss. The optimization problem is formulated as a multi-objective optimal control problem in order to investigate the impact of operational cost factors on optimal operation policy. This is achieved thanks to the use of the analytical approach that exploits Pontryagin's minimum principle. We show that the economically optimal control strategy is to carry out an operation involving saturated (bang-bang or constraint-tracking) control modes and a singular arc. For the most common cases of diafiltration problems, it turns out that the switching of the consecutive control modes can be realized in the state feedback fashion, i.e. the entire optimal operation is defined analytically in the space of process states. We demonstrate the applicability of the presented approach and we illustrate achievable benefits, over traditional control methods for the batch diafiltration processes, on two case studies taken from the literature.     

在逐点状态约束下一个四阶线性系统的时间最优控制

在逐点状态约束下,最优控制问题的求解是很困难的,已有的最大值原理和形态规划理论很难用来求解在逐点状态约束下最优控制问题.本文讨论逐点状态约束下一个四阶线性系统的时间最优控制问题.我们采用转换的方法给出了最优时间与最优控制的具体表达式.     

Robust and optimal attitude control of spacecraft with disturbances

In this paper, a robust and optimal attitude control design that uses the Euler angles and angular velocities feedback is presented for regulation of spacecraft with disturbances. In the control design, it is assumed that the disturbance signal has the information of the system state. In addition, it is assumed that the disturbance signal tries to maximise the same performance index that the control input tries to minimise. After proposing a robust attitude control law that can stabilise the complete attitude motion of spacecraft with disturbances, the optimal attitude control problem of spacecraft is formulated as the optimal game-theoretic problem. Then it is shown that the proposed robust attitude control law is the optimal solution of the optimal game-theoretic problem. The stability of the closed-loop system for the proposed robust and optimal control law is proven by the LaSalle invariance principle. The theoretical results presented in this paper are illustrated by a numerical example.     

Halo orbit mission correction maneuvers using optimal control

This paper addresses the computation of the required trajectory correction maneuvers for a halo orbit space mission to compensate for the launch velocity errors introduced by inaccuracies of the launch vehicle. By combining dynamical systems theory with optimal control techniques, we are able to provide a compelling portrait of the complex landscape of the trajectory design space. This approach enables automation of the analysis to perform parametric studies that simply were not available to mission designers a few years ago, such as how the magnitude of the errors and the timing of the first trajectory correction maneuver affects the correction ΔV. The impetus for combining dynamical systems theory and optimal control in this problem arises from design issues for the Genesis Discovery Mission being developed for NASA by the Jet Propulsion Laboratory.     

参数不确定SGCMG系统的自适应操纵律设计

在单框架控制力矩陀螺(SGCMG)系统操纵律的设计中,如果考虑框架伺服特性,往往假设系统的物理参数是确切已知的.为消除参数的不确定性对操纵性能的影响,设计了一种自适应操纵律.该操纵律可对系统物理参数进行在线估计,并能根据航天器姿态控制给出的角动量(或力矩)指令,直接计算出每个框架驱动系统所需的控制力矩.由于操纵律没有算法奇异,在SGCMG系统不出现运动奇异的情况下,可使操纵误差渐近收敛至零.同时,该操纵律对系统参数变化具有良好的适应性,且形式简单,易于实现.对应用在航天器上的某SGCMG系统的仿真结果表明,上述操纵律是可行的.     

Neighboring optimal control for periodic tasks for systems with discontinuous dynamics

We propose a trajectory-based optimal control method for periodic tasks for systems with discontinuous dynamics. A general method, dynamic programming, suffers from the problem of dimensionality. We use local models of the optimal control law to construct a local controller. We combine a parametric trajectory optimization method and differential dynamic programming (DDP) to find the optimal periodic trajectory in a periodic task. By formulating the optimal control problem with an infinite time horizon, DDP ...